INTERNATIONAL RESEARCH JOURNAL OF ENGINEERING AND TECHNOLOGY (IRJET) E-ISSN: 2395-0056 VOLUME: 05 ISSUE: 09 | SEP 2018 WWW.IRJET.NET P-ISSN: 2395-0072

AERODYNAMIC DESIGN AND PERFORMANCE OF WITH DIFFERENT MACH NUMBERS USING CFD ANALYSIS

Vytla. Jayaprakash1, Alok Kumar Rohit2 , CH.Srinivas3, katrevula srikanth4

1Vytla jayaprakash, Department of Mechanical Engineering, Jain University, Karnataka, India 2DR. Alok Kumar Rohit, Department of Mechanical Engineering, Jain University, Karnataka, India 3Chilagani Srinivas, Department of Mechanical Engineering, Jain University, Karnataka, India 4Katrevula Srikanth, Department of Mechanical Engineering, Jain University, Karnataka, India ------***------Abstract— The exhaust system plays a flagship role 1.1 NOZZLE in aircraft and the design of nozzle have a supersonic cruise mission is optimized for a cruise condition and in takeoff conditions it must give the required quantity of action at other most lynchpin operating points. In contrast, for a vehicle the exhaust nozzle system is to an accelerating mission must provide limited action across the flight envelop as there is not a fixed cruise point were the operates of aircraft the majority of the time. The aerodynamic design and performance analysis of convergent and convergent – divergent nozzle with different lengths 110.236mm and Fig-1: Water nozzle 135.636mm with subsonic and supersonic flow conditions is analyzed using CFD analysis. The comparisons are made for To control the direction of a fluid flow the device is used is pressure distribution, velocity and mass flow rates in 3D called as nozzle it exits (or enters) an enclosed chamber models are done in CATIA and CFD analysis or pipe.

Key words— Nozzles, Cad, Mesh.CFD analysis. 1.2 AERODYNAMIC NOZZLE

1.INTRODUCTION We can metamorphose a into a jet by utilizing the propelling nozzle. Power obtained from the While choosing the nozzles make sure its capabilities with gas turbine exited it can transfer into a high speed your current systems. The perform flow testing to ensure propelling jet by using the nozzles. like you get adequate water and also consider the penetration may have spare and separated propelling nozzle which and reaction force on the firefighter. gives the high speed to propelling jet from the energy from To the extinguish a fire we will use the any nozzle, keep in the air is send through the fan. In addition, by using the mind that actual flow may be affected by many variables, nozzle we can determine how the gas generator and fan such as differences in piping from the pump to the operate as it acts as a downstream restrictor. discharge point, augment friction loss, changes in the types and their individual friction loss, different pump pressures, Propelling nozzles are moving quickly the obtained gas water supply issues and debris passing through the water to subsonic and transonic velocities rely on the power system. So be sure to test your nozzle under ideal setting of engine. The Convergent-divergent (C-D) are the conditions and under poor conditions to decide how it will internal shape which can move quickly the jet to works in both quality and inadequate of water-flow supersonic velocities within the divergent section, whereas situations. a convergent nozzle cannot accelerate the jet beyond sonic speed. By the characteristics of nozzles there are many features are available and uses. The key point is determining which 1.3 Types of nozzle nozzle is right for your needs. To help you make that determination, here’s a breakdown of some of the basic 1) Ejector nozzle nozzle types, and the pros and cons of each. Typically, the smooth-bore nozzle produces the greatest reach/rpm Ejector type of nozzle is used for pumping action of the combination of all nozzles while at the same time using the more scalding, high speed, engine exit entraining to an lowest engine pump ambient air flow. Nozzle manipulates the expansion of the exhaust of engine.

2) nozzle

Nozzles for vectored thrust include fixed geometry Bristol Snidely Pegasus and variable geometry

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3) Rocket nozzle Length 135.636 mm

Rocket motors also used convergent-divergent nozzles, but 3d Sketch these are usually of fixed geometry, to minimize weight.

1.4 MACH

In compressible flow theory the mesh is most flagship parameter, and it comparing with the speed of sound in a fluid (excellent measure of compressibility effects) and the speed at which the fluid is flowing.

1.5 MACH ANGLES

This isentropic wave front is analogous to the oblique shock wave, and the angle between the wave front and the direction of the disturbance's motion is called the Mach Fig-3: Surface model wave angle or Mach angle. CONVERGENT DIVERGENT MODEL 2. INTRODUCTION TO CAD Length 110.236 mm As we know to design of an object in computer is difficult in computer in past days but now a day’s it’s so simple 2d Sketch firstly we know Computer-aided design (CAD) it is software now a day’s it’s made so easy to draw 2D and 3D Surface model diagrams in computers. It’s also called as computer-aided design and drafting (CADD).By the using of Computer The mach numbers or taken from the national aeronautics Aided Drafting which explains the drafting process in and space administration computer. For many of design engineering CADD software Mach number = is a flagship tool by using this software they shows the elegant designs of the objects as per the requirements. The output of CADD is in the form of print or machining THE SPEED OF SOUND C= 343 METERS PER operations. SECOND (M/S)

The required output information is also important for CAD CFD ANALYSIS FOR AERODYNAMIC NOZZLE such as materials, processes, dimensions, and tolerances, according to specific applications. The design curves and CONVERGENT MODEL figures in two-dimensional (2D) space and solids surface in three-dimensional (3D) objects are shown in CAD FLUID –NITROGEN OXIDE software.. The design of geometric objects for object shapes, in particular, is often called computer-aided MODEL LENGTH – 110.236mm geometric design (CAGD).REID FLOW- SUBSONIC FLOW (MACH NUMBER 0.4) 3. 3D MODELING CONVERGENT MODEL

Length 110.236 mm

2d Sketch

Fig-2: Surface model Fig-4: Import model © 2018, IRJET | Impact Factor value: 7.211 | ISO 9001:2008 Certified Journal | Page 952 INTERNATIONAL RESEARCH JOURNAL OF ENGINEERING AND TECHNOLOGY (IRJET) E-ISSN: 2395-0056 VOLUME: 05 ISSUE: 09 | SEP 2018 WWW.IRJET.NET P-ISSN: 2395-0072

Fig-5: Meshed model

Specifying boundaries for inlet, outlet and wall

Select edge → right click → create named section → enter name → inlet

Fig-9: Velocity inlet

Solution → Solution Initialization → Hybrid Initialization →done

Run calculations → no of iterations = 30 → calculate → calculation complete as shown in Fig.9

Fig-6: Inlet

Fig-10: Pressure difference graph

Fig-7: Outlet

Select edge → right click → create named section → enter name → outlet

Wall

Fig-11: Velocity

Fig-8: Inlet and outlet of wall

Select fluid nitrogen oxide

Boundary conditions → select air inlet → Edit → Enter Inlet Velocity → 171.5m/s Fig-12: Reynolds number

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Mass Flow Rate (kg/s) ------

------Net 0.001422882

Inlet 20.427063

Interior-part_1 -411.77686 CONVERGENT DIVERGENT MODEL

Outlet -20.436523 FLUID –NITROGEN OXIDE

Wall 0 MODEL LENGTH – 110.236mm

------

Net -0.0094604492

MODEL LENGTH – 135.636 mm

FLOW- SUPERSONIC FLOW (MACH NUMBER 1.0)

Fig-16: Inlet

Fig-13: pressure

Fig-17: Outlet

Fig-14: velocity

Fig-18: Wall

Select fluid nitrogen oxide

Fig-15: Reynolds number

Mass Flow Rate (kg/s)

------

Inlet 40.853596

Interior-fill.1__ 272.28693

Outlet -40.852173

Wall 0 Fig-19: Select fluid nitrogen oxide © 2018, IRJET | Impact Factor value: 7.211 | ISO 9001:2008 Certified Journal | Page 954 INTERNATIONAL RESEARCH JOURNAL OF ENGINEERING AND TECHNOLOGY (IRJET) E-ISSN: 2395-0056 VOLUME: 05 ISSUE: 09 | SEP 2018 WWW.IRJET.NET P-ISSN: 2395-0072

Wall 0

------

Net 0.026726723

FLOW-SUPER SONIC FLOW (MACH NUMBER 1.0)

Fig-20: Velocity inlet

FLOW- SUBSONIC FLOW (MACH NUMBER 1.0)

Fig-24: Pressure

Fig-21: Pressure

Fig-25: Velocity

Fig-22: Velocity Fig-26: Reynolds number

Mass Flow Rate (kg/s)

------

Inlet 27.960552

Interior-fill.1 -111.17674

Outlet -27.895111 Fig-23: Reynolds number Wall 0 Mass Flow Rate (kg/s) ------Net 0.065441132 Inlet 13.980276 MODEL LENGTH – 135.636mm Interior-fill.1__ -55.600498

Outlet -13.953549

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RESULTS TABLE 1000 CONVERGENT 800

600 Table-1: Subsonic flow 400 200

Length Pressure Velocity Reynolds Mass 0 VELOCITY (mm) (Pa) (m/s) number flow Rate 110.236 135.636 (kg/s) LENGTH (mm) 110.23 89330.5 424.63 67365.2 0.000631 135.63 27530.2 264.28 45528.8 0.00944 Chart-2: Comparison of velocity values for different flows and lengths Table-2: Supersonic flow

Length Pressure Velocity Reynolds Mass flow 150000 (mm) (Pa) (m/s) number Rate (kg/s) 100000

NUMBER 50000 110.236 357324.3 849.31 134740.1 0.0014228 CELL REYNOLDS CELL REYNOLDS 0 135.63 110088. 528.76 91133.5 0.018939 110.236 135.636

LENGTH (mm) CONVERGENT DIVERGENT Table-3: Subsonic flow Chart-3: Comparison of cell Reynolds number values for different flows and lengths Length Pressure Velocity Reynolds Mass (mm) (Pa) (m/s) number flow Rate (kg/s) 0.005

0 110.236 15753.44 340.543 53163.89 0.026726 -0.005 110.236 135.636

135.63 17902.6 372.201 66907.4 0.01281 (Kg/S) -0.01 -0.015

Table-4: Supersonic flow MASS FLOW RATE -0.02 LENGTH (mm) Length Pressure Velocity Reynolds Mass flow (mm) (Pa) (m/s) number Rate (kg/s) Chart-4: Comparison of mass flow rate values for different 110.23 62972.7 681.19 106358.4 0.0654 flows and lengths 135.636 71.557.2 747.09 133843.5 0.0266 Convergent divergent model

Convergent model 80000

60000 100000 40000 80000 20000 60000 40000 PRESSURE 0

PRESSURE 20000 110.236135.636 0 110.236 135.636 LENGTH (mm)

LENGTH (mm) Chart-5: Comparison of pressure values for different flows and lengths Chart-1: Comparison of pressure values for different flows and lengths

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decreases. As per the Bernoulli’s equation the diminish of pressure as augment of velocity. Mass flow rates are 800 increasing by increase of mach numbers and increase of 600

lengths. The values are increasing by increasing the length 400 of the nozzle. This is due to fact that by increasing the lengths the fluid is compressed inside the nozzle. The 200 pressure distribution, velocities are more under VELOCITY 0 supersonic flow conditions due to high inlet velocities. So it 110.236 135.636 can be concluded that increasing mach numbers and lengths yields to better performance of nozzle. LENGTH (mm)

REFERENCES Chart-6: Comparisons of velocity values for different flows [1] Deng Qingfeng, ZhengQun, Yue Guoqiang, Zhang Hai, and lengths Luo Mingcong, “Using a Pressure Controlled Vortex Design Method to Control Secondary Flow Losses in a Turbine Stage", Chinese Journal of Aeronautics, 2013, 26(5), pp 1125–1134 150000 100000 [2] John D Denton, "Some Limitations of Turbo machinery 50000 CFD”, Proceedings of ASME Turbo Expo 2010: Power for NUMBER Land, Sea and Air, 2010, PaperGT2010-22540

0 CELL REYNOLDS CELL REYNOLDS 110.236 135.636 [3] Prathapanayaka ET. al, "Design and Development of LENGTH (mm) 385kW turbine stage for Small Gas Turbine Engine", Project Document, PD-PR/2015/1000, 2015, Division, National Laboratories, Bangalore.

[4] Hany Moustapha, Mark F.Zelesky, Nicholas C.Baines, Chart-7: Comparison of cell Reynolds number values for David Japikse; Axial and Radial Flow Turbines, Published different flows and lengths by Concepts NREC, 2003

0.08 [5] NASA SP-290, “Turbine Design and Application”, 1994 0.06 [6] Anderson JD, [2001], Fundamentals of Aerodynamics,

0.04 0.02 3rd Edition, pp.532-537, pp.555-585. 0 (Kg/S) 110.236 135.636 [7] Anderson JD, [1982], Modern Compressible Flow with Historical, pp.268-270, pp.282-286.

MASS MASS FLOW RATE LENGTH (mm) [8]Shapiro, AH, [1953], the Dynamics and Thermodynamics of Compressible Fluid Flow, Vol.1, pp. 294-295. Chart-8: Comparison of mass flow rate values for different flows and lengths

CONCLUSIONS

The aerodynamic design and performance analysis of convergent and convergent – divergent nozzle with different lengths 110.236mm and 135.636mm with subsonic and supersonic flow conditions is analyzed. The comparisons are made for pressure distribution, velocity and mass flow rates.

3D models are done in CATIA and CFD analysis is done in Ansys.

By observing the results, the augment of velocity and diminish of Pressure along the length of the nozzle accepts little bit increasing during the shocking. However, the augment will not show any significant to the total pressure

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